GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il)
GOE 324 (HANSA-BRANDENBURG) AIRFOIL - Gottingen 324 (Hansa-Brandenburg) airfoil
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(goe324-il) GOE 324 (HANSA-BRANDENBURG) AIRFOIL Gottingen 324 (Hansa-Brandenburg) airfoil Max thickness 13.1% at 29.8% chord. Max camber 5.9% at 29.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 324 (HANSA-BRANDENBURG) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0119800 0.0322000
0.0242600 0.0452000
0.0489400 0.0651000
0.0737200 0.0787000
0.0985200 0.0905100
0.1482500 0.1072200
0.1980900 0.1171300
0.2979600 0.1251600
0.3980600 0.1192900
0.4983000 0.1044200
0.5986500 0.0826600
0.6990400 0.0587900
0.7994000 0.0365300
0.8997200 0.0173700
0.9498600 0.0085800
1.0000000 0.0012000
0.0000000 0.0000000
0.0127600 -.0161900
0.0252800 -.0170900
0.0502500 -.0155800
0.0752400 -.0142300
0.1002100 -.0130000
0.1501700 -.0102500
0.2001400 -.0084400
0.3001000 -.0062100
0.4000700 -.0045800
0.5000700 -.0040500
0.6000700 -.0040200
0.7000700 -.0044900
0.8000600 -.0039600
0.9000500 -.0028300
0.9500300 -.0020100
1.0000000 -.0012000
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Polars for GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe324-il | 50,000 | 9 | 8.3 at α=-3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 50,000 | 5 | 20 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 100,000 | 9 | 33.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 100,000 | 5 | 49.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 200,000 | 9 | 70.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 200,000 | 5 | 74.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 500,000 | 9 | 108.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 500,000 | 5 | 104.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 1,000,000 | 9 | 136.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 1,000,000 | 5 | 124 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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